Self-propelled rocket and collapsible rocket launch stand for use in providing the controlled occurence of an avalanche or a mud slide

ABSTRACT

A self-propelled and constant-acceleration rocket for use in triggering an avalanche includes a hollow cylindrical body member having an interior volume, an open top end, and an open bottom end whose exterior surface includes a plurality of flight guidance fins. A partition wall divides the interior volume into an upper volume and a lower volume. An explosive payload is mounted within the upper volume, and a nose cone having a circular and planar tip closes the open top end of the body member. A rocket motor is mounted within the lower volume. The rocket has a center of gravity and a center of pressure that are both located on the rocket&#39;s central axis and within the lower volume. The center of gravity is located closer to the open top end than is the center of pressure. A collapsible launch stand holds the rocket in a launch tube for launching of the rocket. Adjustment of a pair of launch tube support members provides for adjustment of the rocket&#39;s launch angle.

CROSS-REFERENCE TO RELATED APPLICATION

[0001] This application claims the benefit of co-pending U.S.Provisional Patent Application Ser. No. 60/214,869, filed Jun. 28, 2000and entitled SELF-PROPELLED AVALANCHE/MUDSLIDE CONTROL APPARATUS.

BACKGROUND OF THE INVENTION

[0002] 1. Field of the Invention

[0003] This invention relates to the control of snow avalanches andmudslides. More specifically, this invention provides a self-propelledrocket and a collapsible launch stand that can be easily transported toa desired location in order to produce snow avalanches or mudslides in acontrolled manner.

[0004] 2. Description of the Related Art

[0005] As used herein, the term avalanche is intended to mean a largemass of snow, ice, earth, mud, rock, or the like, that swiftly movesdown an incline such as a mountain side or over a precipice.

[0006] In attempting to prevent dangerous avalanches, explosive devicesare conventionally propelled into a mountainside in order tocontrollably initiate or trigger an avalanche, thus reducing the risk ofa naturally occurring, dangerous and uncontrolled avalanche.

[0007] Conventionally, a variety of mechanisms have been used to attemptto trigger an avalanche in a controlled manner. For example, handcharges are lit and then manually thrown into the desired hillside. Thismethod can subject personnel to risks of injury.

[0008] U.S. Pat. No. 5,872,326 discloses an apparatus for triggering anavalanche or the like. In the device of this patent, an explosive chargeis made up of an explosive, a detonator, and a lighting mechanism fortriggering the detonator. The explosive charge is placed in a tube witha propelling charge. A pulling element operates to trigger the lightingmechanism after the explosive charge has been propelled out of the tube.

[0009] Guns can be used to trigger an avalanche, an example of which isan avalanche launch gun, such as the “Avalauncher.” The Avalauncheroperates like a gun in that a charge is shot into the air by way of aninitial force, whereupon the charge travels a distance which is, atleast in part, a function of the initial force that is applied to thecharge.

[0010] What is needed is a self-propelled rocket, a collapsible launchstand, and method for triggering an avalanche wherein the rocket isself-propelled at a substantially constant acceleration to travel in asubstantially line of sight path to a point of impact. It is againstthis background that various embodiments of the present invention weredeveloped.

SUMMARY OF THE INVENTION

[0011] This invention provides a self-propelled rocket and collapsiblelaunch stand that are easily transported by way of a snowmobile,backpack, or the like to a site whereat naturally occurring avalanchesare known to occur. Upon setting up of the launch stand at anappropriate angle and the placement of a launch tube thereon, theself-propelled rocket is placed into the launch tube, a rocket motorwithin the rocket is ignited, and the rocket proceeds to a somewhatdistant hillside to then explode and induce an avalanche thereon in acontrolled manner.

[0012] As a feature of the invention, a second or redundant rocket motormay be provided such that, after a time delay that is indicative offailure of the first rocket motor to ignite, the second rocket motorignites whereupon the rocket proceeds to a somewhat distant hillside tothen explode and induce an avalanche in a controlled manner.

[0013] The self-propelled rocket moves at a constant accelerationrocket. The rocket includes a hollow cylindrical body member having aninterior volume, an open top end, and an open bottom end whose exteriorsurface includes a plurality of flight guidance fins.

[0014] The inner volume of the hollow cylindrical body provides an uppervolume and a lower volume. As a feature of the invention, a partitionwall is provided to divide this interior volume into an upper volume anda lower volume.

[0015] An explosive payload is mounted within the upper volume, and anose cone having a circular and planar tip closes the open top end ofthe body member. A rocket motor is mounted within the lower volume. Therocket has a center of gravity and a center of pressure that are bothlocated on the rocket central axis and within the lower volume. Thecenter of gravity is located closer to the open top end than is thecenter of pressure.

[0016] A collapsible launch stand holds the rocket in the launch tubefor launching of the rocket. Adjustment of a pair of launch tube supportmembers provides for adjustment of the rocket launch angle.

[0017] The rocket center of gravity is located closer to the cone end ofthe rocket than is the rocket center of pressure, and the tip of thecone is a flat plane that extends generally perpendicular to the rocketcentral axis; i.e., generally perpendicular to the rocket direction offlight. With these characteristics, and as a result of the rocket finsand the rocket velocity at the time that motor burnout occurs, it isensured that upon rocket motor burn out occurring, the rocket drops in adeclining trajectory downward and into the hillside.

[0018] These and other features and advantages of the invention will beapparent to those of skill in the art upon reference to the followingdetailed description which description makes reference to the drawing.

BRIEF DESCRIPTION OF THE DRAWING

[0019]FIG. 1 is a side view of a self-propelled rocket in accordancewith the invention, the rocket internally having an explosive payloadthat is adapted to detonate upon impact with a slope having a propensityto naturally generate an avalanche.

[0020]FIG. 2 is a side view of a manually-lightable igniter, or fuse,that operates to ignite a rocket motor that is within the FIG. 1 rocket.

[0021]FIG. 3 is a side view of a mobile launch stand for use inpositioning the FIG. 1 rocket prior to launch of the rocker, the launchstand being shown in its collapsed position.

[0022]FIG. 4 is a top view of the FIG. 3 collapsed launch stand.

[0023]FIG. 5 illustrates the FIG. 1 rocket within a launch tube that ispositioned on the FIG. 3 launch stand, the launch stand now being in itsopened or upright position, and the launch tube loosely resting againsta pair of vertically extending support members that are a portion of thelaunch stand.

DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0024] The following embodiments and examples of the present inventionare illustrative of the invention, and are not restrictive of the spiritand scope of the invention. Modifications that come within the meaningand range of present and after developed equivalence are to be includedwithin the spirit and scope of the invention. While the invention willbe shown and described with reference to a preferred embodiment thereof,it will be understood by those skilled in the art that various changesin form and detail may be made without departing from the spirit andscope of the invention.

[0025] Referring to FIG. 1, rocket 10 in accordance with the presentinvention includes a nose cone 11, a body tube 12 that is adapted tointernally hold an explosive payload 13, a rocket motor 14, and aplurality of external flight guidance fins 15 that are mounted on bodytube 12 at the opposite end from nose cone 11.

[0026] The rocket nose cone 11 is positioned at the top end 16 of rocket10, while rocket motor 14 is positioned generally at the bottom end 17of rocket 10. As will be explained below, explosive payload 13 ispositioned toward the top end 16 of rocket 10. When rocket 10 hitssnow/mud/ground, explosive payload 13 detonates to start an avalanche ina controlled manner.

[0027] As shown in FIG. 1, nose cone 11 is generally conically-shapedand extends from an interface end 18 that is adapted to connect to bodytube 12 to a top end 19 that comprises a generally flat plane thatextends perpendicular the central axis 20 of rocket 10.

[0028] The flat top end 19 of nose cone 11 is provided so that whenrocket 10 physically contacts or engages the snow, mud or the ground,nose cone 11 provides a larger contact area 19 against thesnow/mud/ground when compared to a non-flat top cone end, such as aconventional pointed end that terminates at a sharp tip. In one example,nose cone 11 of the present invention was about 2.75-inches long (seedimension 24), had a 1.5-inch diameter area at its flat top end 19, andwas formed from molded plastic.

[0029] The top end 21 of the rocket body tube 12 is mechanically coupledto the interface end 18 of nose cone 11. Body tube 12 provides atwo-part internal volume, or area 22, for the storage of explosivepayload 13, provides a bottom end external and cylindrical surfaceregion 23 for the attachment of a plurality of flight guidance fins 15,and provides a lower internal volume or area 25 for housing rocket motor14.

[0030] Body tube 12 has a top end 21 and a bottom end 23, and in oneexample, body tube 12 was a generally circular cylinder having acentrally-located axis 20, and having a hollow interior 22 that extendedtherethrough. In one example, body tube 12 was 14-inches in axiallength, and was made of fiber wound plastic, or like material. Thebottom end 23 of body tube 12 further includes has a plurality of slots(not shown) that are adapted to receive rocket guidance fins 15 (forexample, four slots for four fins 15). These slots extend parallel toaxis 20 and are cut into the bottom end 23 of body tube 12, each slotbeing, for example, {fraction (1/16)} of an inch in width. These slotscan be equally spaced about the periphery of the body tube, for exampleat 90-degree intervals.

[0031] Furthermore, body tube 12 is adapted to house rocket motor 14 atits bottom end 23 and within lower volume 25. In one example, body tube12 had an outer diameter of 2.2-inches and an inner diameter of2.1-inches, thus providing a wall thickness of 0.1-inch.

[0032] In one example, rocket motor 14 was positioned and held withinthe interior 22 of body tube 12 through the use of O-rings or likestructures (not shown), which non-movably secure rocket motor 14 withinbody tube 12.

[0033] Further, fins 15 (in one example comprising four fins made ofmolded plastic) are secured within the slots formed within body tube 12through the use of an adhesive substance such as glue, or rivets orother securement means.

[0034] In order to position explosive payload 13 within body tube 12, arigid partition or bulkhead 30 may be positioned within the interior 22of body tube 12 at a desired location along axis 20. Bulkhead 30 dividesvolume 22 into a lower volume 25 and an upper volume 26. Partition 30comprises a flat and rigid disk whose plane extends generallyperpendicular to axis 20. In one example, partition 30 was a soliddisk-shaped member that was positioned within body tube 12 at a desiredlocation, and then secured within body tube 12 using, for example,rivets or an adhesive substance, such as glue.

[0035] The axial position of partition 30 is dependent upon the size ofexplosive payload 13, and this positioning of partition 30 affects howrocket 10 travels after rocket motor 14 has burned out. Preferably,partition 30 is positioned between motor 14 and explosive payload 13,and generally towards the top end 21 of body tube 12.

[0036] Rocket motor 14 provides a means to propel rocket 10 duringflight, preferably at a substantially constant acceleration withincreasing velocity, in order to deliver explosive payload 13 to adesired location. In one example, rocket motor 14 was an H45W rocketmotor by Aerotech Consumer Aerospace of Las Vegas this rocket motorhaving a 15 to 18 pound initial thrust (preferably an 18 pound initialthrust) and preferably this rocket motor operates for 7.1 seconds untilburnout, with an average thrust of approximately ten pounds beingdistributed over the 7.1 seconds of operation.

[0037] In one example, a rocket 10 with such a rocket motor 14 traveleda distance of one mile, in an approximately line of sight flight path,when fired at a 35-degree angle relative to a horizontal plane. In oneexample, rocket motor 14 had an axial length of 7-inches and an outerdiameter of 1.5-inches. By way of example, rocket 10 had a dimension 27of 17.5-inches and a dimension 28 of 16.75-inches.

[0038] In order to reduce the amount of travel of rocket 10 afterburnout of motor 14 occurs, and in accordance with one embodiment of thepresent invention, it was desirable to use fins 15 of a small size, andit was desirable to position explosive payload 13 within body tube 12 ina forward position. By reducing the amount of travel of rocket 10 afterengine burnout occurs, the risk that rocket 10 will travel a substantialdistance after burnout, and thereby possibly miss the desired target, isreduced. Preferably, rocket 10 travels a distance that is a function, inpart, of the size of rocket motor 14, the burn time of motor 14, and theparticular dimensions and configurations of rocket 10.

[0039] In one example, four equally-spaced fins 15 were provided toassist rocket 10 in flying in a stable manner and in a relative straightline. Each fin 15 had an approximate thickness of {fraction(1/16)}-inch, a width of 1.365-inches (measured perpendicular to axis20), and a length of 6-inches (measured parallel to axis 20). Each fin15 had a slanted leading edge 31 approximately 2-inches long and a2-inch long slanted trailing edge 32 that axially-extended approximately1-inch beyond the bottom end 23 of body tube 12 and rocket motor 14.This form of a slanted trailing edge 32 has been found to improve theflight stability of rocket 10, and the slanted trailing edges 32 havebeen found to reduce deterioration of fins 15 due to heat generated byrocket motor 14.

[0040] Further, in one example, explosive payload 13 was positionedrelatively forward within body tube 12, as is shown in FIG. 1, in orderto reduce an amount of travel of rocket 10 after burnout of rocket motor14 has been completed. The axial position of explosive payload 13 withinbody tube 12 is governed, in part, by the position of theabove-mentioned partition/bulkhead 30 by the axial length of explosivepayload 13, and by the weight of explosive payload 13.

[0041] In one example, a 8 ounce explosive payload 13 was 1⅝-inches indiameter and 4¾ inches long; and for this explosive payload 13 partition30 was positioned 5½-inches from the top end 21 of body tube 21,resulting in a distance traveled of 1.25 miles by rocket 10.

[0042] In another example, a 10 ounce explosive payload 13 was 2-inchesin diameter and 4¾-inches long; and partition 30 was positioned5⅘-inches from the top end 21 of body tube 12, to thereby produce traveldistance of 1.00 miles by rocket 10.

[0043] In another example, a 12 ounce explosive payload 13 was 2¼-inchesin diameter and 4¾-inches long, partition 30 was positioned 6 inchesfrom the top end 21 of body tube 12, to produce a travel distance of0.85 miles by rocket 10.

[0044] In another example, for an explosive payload 13 of 8, 10, or 12ounce, partition 30 was positioned at from 5¾-inch to 6¾-inch from thetop end 21 of body tube 12.

[0045] It is understood that the dimensions provided herein are by wayof example only, and that the particular structure and positioning ofeach of the elements of rocket 10 for triggering an avalanche is amatter of choice depending upon the particular implementation.

[0046] Furthermore, the flight stability and distance that rocket 10travels after rocket motor 14 has burned out is also governed by therelative positions of the center of pressure 34 and the center ofgravity 35 of rocket 10. Preferably, the center of pressure 34 islocated on axis 20, within lower volume 25, and toward the bottom end 17of rocket 10, whereas the center of gravity 35 is located on axis 20,within lower volume 25, and toward the top end 16 of rocket 10. That is,the center of pressure 34 is below the center of gravity 35.

[0047] The axial position of the center of pressure 34 is controlled, inpart, by the size of fins 15 and by the position of fins 15 along theaxial length 20 of body tube 12, by the diameter of body tube 12, and bythe shape of nose cone 11. In one example, the rocket center of pressure34 was 7-inches above the bottom end 23 of body tube 12.

[0048] The position of the rocket center of gravity 35 depends, in part,on the position of explosive payload 13 within body tube 12. Preferably,center of gravity 35 is above center of pressure 34 by a distance thatis approximately equivalent to the outer diameter of body tube 12. Inone example, body tube 12 had an outer diameter of 2.2-inches.

[0049] By positioning the center of gravity 35 above the center ofpressure 34, rocket 10 of the present invention is “nose heavy.” Thus,upon burnout of motor 14 occurring, rocket 10 quickly falls to theground, with nose cone 11 striking the ground/avalanche/mud with anacceleration that is approximately equal to the acceleration of rocket10 before motor burn out occurred, thereby detonating explosive payload13.

[0050] Explosive payload 13, in one example of the present invention,comprised a main charge 40 and a cap detonator 41. Main charge 40 was abooster explosive having an ultra high explosive rating with adetonation velocity of approximately 26,000 feet per second. Main charge40, when detonated, was responsible for initiating an avalanche.

[0051] Cap detonator 41 was positioned proximate to main charge 40, andwas preferably secured to the top end of main charge 40, as is shown inFIG. 1, toward the top end 21 of body tube 12. Cap detonator 41 is ahigh explosive that ignites with as much force as is required todetonate main charge 40.

[0052] In operation, and after rocket motor 14 has burned out, rocket 10decelerates downward and into the ground/snow/mud, with nose cone 11pointing down, and with nose cone 11 being the first element of rocker10 to contact the ground/snow/mud. Because of the positioning of capdetonator 41 toward the top end 16 of rocket 10, with main charge 40being positioned behind cap detonator 41, upon impact, main charge 40(which weighs more than cap detonator 41) slides forward within bodytube 12 and crushes cap detonator 41. Cap detonator 41 then ignites andcauses main charge 40 to detonate, which then initiates an avalanche. Asmall primer is associated with cap detonator 41. This primer explodescap detonator 41, whereupon main charge 40 explodes. In other words, theexplosion sequence comprises an impact, detonation of the primer,detonation of cap detonator 41, and detonation of main charge 40.

[0053] An ignition system for igniting rocket motor 14 is also disclosedherein. In one example (not shown), a conventional battery and anelectric squib were used to ignite the rocket motor.

[0054] As an alternative for use where allowed by government regulation,FIG. 2 shows a fuse assembly 45 in accordance with one embodiment of theinvention for igniting rocket motor 14. Preferably, fuse assembly 45includes a fuse portion 46 and a portion 47 of heat-shrink material thatsurrounds a portion of fuse 46. Fuse 46 is preferably a black powderfuse that is made of string-like material (i.e., candlewick cotton),approximately ⅛-inch in diameter and 11¼-inches long.

[0055] The length of heat-shrink material 47 is preferably 6-incheslong. A length 48 of fuse 46 is bent along the outer perimeter ofheat-shrink material 47. Because a portion of fuse 46 is containedinside of heat-shrink material 47, once the end 59 fuse 46 is lit, firewithin the lit fuse travels efficiently toward the top end 50 of fuseassembly 45.

[0056] Furthermore, fuse 46 preferably extends from the back portion 51of heat-shrink material 47 by approximately 10-inches, which 10-inchextension provides an ignition delay period. Fuse 49 preferably burns ata rate of approximately 1-inch every 1.4 seconds.

[0057] In one example, the top end 50 of fuse assembly 45 was dippedinto a fire fluid to promote the rapid and instantaneous combustion ofthe top end 50 of fuse 49 proximate rocket motor 14. It has been foundthat a more instantaneous and complete combustion of the top end 50 offuse assembly 45, proximate rocket motor 14, promotes improved lightingand firing of rocket motor 14. In one example, the fire fluid was anacetone-based solution generally described in “The Chemistry ofPyrotechnics” by John A. Conkling, 1985, the disclosure of which isexpressly incorporated herein by reference.

[0058] Preferably, after the top end 50 of the assembly 45 is immersedin the fire fluid, a thin line of the fire fluid is dripped along theouter perimeter of heat-shrink material 47, approximately half way downits length. Fuse assembly 47 is then permitted to dry.

[0059] Upon fuse assembly 45 being formed as above described, and afterrocket 10 has been positioned on launch stand 55 (shown in FIGS. 3-5 anddescribed below), the top end 50 of fuse assembly 45 is inserted into anopening (not shown) that is within rocket motor 14, this opening beingadapted to receive a fuse. Fuse assembly 45 can then be manually lit atthe end 49 that is opposite to rocket motor 14, in order to igniterocket motor 14 and propel rocket 10 toward a desired target.

[0060] Referring now to FIGS. 3-4, a launch stand 55 in accordance withthe present invention is shown. Launch stand 55 includes a pair ofparallel-extending and rigid launch tube support members 56, about34-inches long, whose ends 57 are pivotally coupled to the ends 58 of apair of parallel extending and rigid positioning members 59 that areabout 34-inches long.

[0061] Launch tube support members 56 are adapted to loosely support alaunch tube 60 (see FIG. 5) having a rocket 10 positioned therein. Inthis position, the bottom end 36 of launch tube 60 rests against a pairof upright support members 37.

[0062] At one end 61, launch tube support members 56 are rotatablyconnected to a flat base plate 62 by way of a dowel pin 63. At the otherend 57, launch tube support members 56 are rotatably coupled topositioning members 59 by way of a dowel pine 64.

[0063] The ends 66 of positioning members 59 extend between a parallelset of rails 65 that are non-movably secured to base plate 62. Rails 65act as guide members on which the ends 66 of positioning members 59 canslide.

[0064] In one example, a plurality of openings 67 were provided withinrails 65 to securely and adjustably position the ends 66 of positioningmembers 59 relative to rails 65 and base plate 62. Alternatively,positioning members 59 can be adjustably secured to rails 65 by the useof one or more clamps (not shown).

[0065] By moving the ends 66 of positioning members 59 relative to rails65 changes the position of the pivot point at which launch tube supportmembers 56 are connected to positioning members 59 (i.e., at dowel pin64). In this way, this pivot point can be moved up or down to providevarious angles for launch tube 60 relative to base plate 62.

[0066] A portion of launch tube support members 56 supports launch tube60, and a rocket 10 that is located therein, after launch stand 55 hasbeen appropriately set and secured to achieve a desired angle for launchtube 60, as shown in FIG. 5.

[0067] Launch stand 55, preferably in the collapsed position shown inFIGS. 3 and 4, is adapted to be towed behind a snowmobile, or to bemounted in or on a stretcher that is connected to a snowmobile, so thatlaunch stand 55 is easily moveable to a location that is susceptible toavalanches. Launch stand 55 can also be adapted to be carried usingshoulder straps (not shown), or by way of a backpack.

[0068] In one example, base plate 62 of launch stand 55 was 5½ feet longand 2 feet wide.

[0069] As shown in FIG. 5, launch tube 60 is preferably a hollowcylindrical tube having a closed bottom that can be made of similarmaterials as body tube 12 of rocket 10. Preferably, launch tube 60 has a4¾-inch inner diameter, and preferably the difference between the innerdiameter of launch tube 60 and the outer dimensions of rocket 10(including fins 15) is 0.015-inch.

[0070] In overall operation, rocket 10 is formed and explosive payload13 positioned at a desired location within body tube 12. Launch stand 55is placed and oriented in a proper position and at a proper angle forthe firing of rocket 10. Launch tube 60 is then placed on launch stand55, and rocket 10 is inserted within launch tube 60. An ignitionassembly 45 is then inserted into rocket engine 14 and the ignitionassembly is activated; for example, a fuse is lit. After rocket motor 14is ignited, rocket 10 travels, in one example, with substantiallyconstant acceleration and in a substantially straight line of sight.When rocket motor 14 burns out, rocket immediately 10 falls and hits theground/snow/mud. Due to the inertia that is created by the force ofrocket motor 14, main charge 40 now slides forward within body tube 12and crushes cap detonator 41 and its primer, thus igniting cap detonator41, and thus detonating main charge 40. The resulting explosion thentriggers an avalanche.

[0071] It is believed that the blast created by rocket 10 is directionaland in the same direction as the flight of the rocket. If desired, maincharge 40 may be constructed and arranged to provide a desired directionof blast upon impact.

[0072] While the present invention has been described and shown in termsof a rocket 10 having particular dimensions and an explosive payload 13having particular weights and dimensions, and a fuse assembly 45 and alaunch stand 55 having particular characteristics, it is understood thatthese details are by way of example only and that changes in rocket 10,explosive payload 13, fuse assembly 45, and/or launch stand 55 are amatter of choice within the spirit and scope of the invention.

[0073]FIG. 6 is a partially sectioned view of the explosive payload 13assembly. A percussion primer 41A and a shock tube 41B interact with thehigh-explosive main charge 40 as described.

[0074]FIG. 7 is an end view of launch tube 60A with a rocket 60A inplace. In this particular example, guide rails 81-84 run the length oftube 60A and support the outer periphery of rocket 10A during itsoutward travel although these rails are somewhat spaced from the rocketIOA outer surface. Supports members 81-84 are preferably offset fromfins 15 as shown.

[0075] If desired, a secondary or redundant explosive charge can beincluded within the body of rocket 10. This charge could be located atthe top end of the rocket motor and configured to explode apredetermined time period after impact or launch of the rocket. Therocket would then be buried in the snow, mud, etc. and produce thedesired end result. Thus, if the explosive payload 13 should fail, thesecondary charge would detonate after the time delay exploding bothitself and the primary payload 13. Conversely, the secondary chargecould likewise be detonated by payload 13 when it successfullydetonates.

[0076] While the methods disclosed herein has been described and shownwith reference to particular steps performed in a particular order, itwill be understood that these steps may be combined, sub-divided, orre-ordered to form an equivalent method without departing from theteachings of the present invention. Accordingly, unless specificallyindicated herein, the order and grouping of the steps is not alimitation of the present invention.

What is claimed is:
 1. A self-propelled rocket for use in triggering an avalanche, comprising: a hollow cylindrical body member having a central axis, an interior volume that includes an upper volume and a lower volume, an open top end, and an open bottom end whose exterior surface includes a plurality of flight guidance fins; an explosive payload mounted within said upper volume; a nose cone mounted to close said open top end of said body member and having a circular planar tip that extends generally perpendicular to said central axis; a rocket motor mounted within said lower volume; and said rocket having a center of gravity and a center of pressure that are both located on said central axis and within said lower volume, said center of gravity being located closer to said open top end of said body member that is said center of pressure.
 2. The rocker of claim wherein said rocket motor is operable to impart a substantially constant acceleration and a generally line of sight flight to said rocket.
 3. The rocket of claim 2 wherein said rocket motor is activated by way of an ignition means having a time delay.
 4. The rocket of claim 3 wherein said explosive payload comprises: a main charge mass mounted within said upper volume; and a cap detonator of smaller mass than said main charge mounted within said upper volume intermediate said main charge and said nose cone.
 5. The rocket of claim 4 wherein said rocket motor provides from about 5 to about 18 pounds thrust to said rocket.
 6. The rocket of claim 5 wherein said rocket motor operates to impart a velocity of about 26,000 feet per second to said rocket.
 7. The rocker of claim 6 wherein: said body tube is about 17-inches long and has an external diameter of about 2-inches; said nose cone is about 3-inches long; and a diameter of said circular planar tip of said nose cone is about 1.5-inch.
 8. The rocket of claim 1 wherein: said center of pressure is located about 7-inches from said bottom end of said body tube; and said center of pressure is located about 5-inches from said bottom end of said body tube.
 9. The rocket of claim 8 wherein said rocket motor provides from about 5 to about 18 pounds thrust to said rocket.
 10. The rocket of claim 9 wherein said rocket motor operates to impart a velocity of about 26,000 feet per second to said rocket.
 11. The rocket of claim 1 including: a partition wall mounted within said body member and dividing said interior volume into said upper volume and said lower volume; said explosive payload being mounted within said upper volume generally adjacent to said partition wall; and said rocket motor being mounted within said lower volume generally adjacent to said open bottom end of said body tube.
 12. The rocker of claim 11 wherein said rocket motor is operable to impart a substantially constant acceleration and a generally line of sight flight to said rocket.
 13. The rocket of claim 12 wherein said explosive payload comprises: a main charge mass mounted within said upper volume adjacent to said partition wall; and a cap detonator of smaller mass than said main charge mounted within said upper volume intermediate said main charge and said nose cone.
 14. The rocket of claim 13 wherein said rocket motor provides from about 5 to about 18 pounds thrust to said rocket.
 15. The rocket of claim 14 wherein said rocket motor operates to impart a velocity of about 26,000 feet per second to said rocket.
 16. The rocker of claim 15 wherein: said body tube is about 17-inches long and has an external diameter of about 2-inches; said nose cone is about 3-inches long; and a diameter of said circular planar tip of said nose cone is about 1.5-inch.
 17. The rocket of claim 11 wherein: said center of pressure is located about 7-inches from said bottom end of said body tube; and said center of pressure is located about 5-inches from said bottom end of said body tube.
 18. The rocket of claim 17 wherein said rocket motor provides from about 5 to about 18 pounds thrust to said rocket.
 19. The rocket of claim 18 wherein said rocket motor operates to impart a velocity of about 26,000 feet per second to said rocket.
 20. In combination with the rocket of claim 1, a collapsible launch stand, comprising: a flat base plate; a pair of spaced and parallel extending support members extending generally vertically upward from said base plate; a pair of spaced and parallel-extending linear launch tube support members; each launch tube support member having one end pivotally connected to said base plate generally adjacent to one of said support members; each launch tube support member having an opposite end; a pair of spaced and parallel extending linear launch tube-positioning members; each launch tube positioning member having one end pivotally connected to said opposite end of one of said launch tube support members; each launch tube positioning member having an opposite end; coupling means associated with said base plate for selectively coupling said opposite ends of said launch tube positioning members to said base plate at a desired common distance from said one end of said launch tube support members; and a launch tube loosely sitting on said launch tube support members so as to engage said support members.
 21. The collapsible launch stand of claim 20 wherein: said base plate is about 5 feet long and about 2 feet wide; said launch tube support members are about 3 feet long and extend in a direction of the length of said base plate; and said launch tube positioning members are about 3 feet long and extend in said direction of said length of said base plate.
 22. The collapsible launch stand of claim 21 wherein: said rocket is loosely positioned within said launch tube; and said selectively coupling of said opposite ends of said launch tube positioning members to said base plate at a desired common distance from said one end of said launch tube support members operates to determine a launch angle of said rocket.
 23. A collapsible launch stand for in launching a self-propelled rocket at a desired angle, comprising: a flat base plate; a pair of spaced and parallel extending support members extending generally vertically upward from said base plate; a pair of spaced and parallel extending linear launch tube support members; each launch tube support member having one end pivotally connected to said base plate generally adjacent to one of said support members; each launch tube support member having an opposite end; a pair of spaced and parallel extending linear launch tube positioning members; each launch tube positioning member having one end pivotally connected to said opposite end of one of said launch tube support members; each launch tube positioning member having an opposite end; coupling means associated with said base plate for selectively coupling said opposite ends of said launch tube positioning members to said base plate at a desired common distance from said one end of said launch tube support members; a launch tube loosely sitting on said launch tube support members so as to engage said support members; and a self-propelled rocker loosely contained within said launch tube.
 24. A method of inducing an avalanche to occur on a hillside that has a propensity to naturally generate avalanches, comprising the steps of: providing a self-propelled and constant acceleration rocket having a hollow cylindrical body member with a partition wall that divides said body member into an upper volume and a lower volume; providing an explosive payload mounted within said upper volume; providing a nose cone having a circular and planar tip mounted at an opposite end of said upper volume from said partition wall; providing a rocket motor mounted within said lower volume; said rocket being constructed and arranged to have a center of gravity and a center of pressure that are located a central axis of said rocket and within said lower volume; said center of gravity being located closer to said nose cone end than is said center of pressure; providing a collapsible launch stand for holding said rocket in a launch tube for launching said rocket; providing launch tube support members for adjustment of a launch angle for said launching rocket; transporting said rocket and said launch stand to said hillside; opening said launch stand and adjusting said launch angle; placing said rocket into said launch tube; and activating said rocket motor. 